Flying object

Abstract

[Problem] To provide a flying object or the like capable of improving the strength of a whole rotor frame without thickening the rotor frame. [Solution] One aspect of the present invention provides a flying object comprising an aircraft body, a plurality of rotor frames, a motor, and a rotor, wherein: the aircraft body supports the plurality of rotor frames; the plurality of rotor frames have contact parts that are contacts to which a plurality of frames including the rotor frames are connected; the motor is supported at the contact parts and is configured to be able to transmit, to the rotor, a driving force for rotating the rotor; and the rotor is supported at the contact parts and is configured to be able to rotate using the driving force.

Description

flying object

[0001] The present invention relates to an air vehicle.

[0002] Patent Document 1 discloses an unmanned aerial vehicle.

[0003] This unmanned aerial vehicle is an unmanned aerial vehicle with multiple rotors, with multiple arms extending radially from the center of the body, each arm having a floating part extending downward from the arm, and each floating part having an air chamber, which is a hollow, sealed space, inside.

[0004] Japanese Patent Application Laid-Open No. 2019-055775

[0005] However, as described in Patent Document 1, conventional arms (rotor frames) have a cantilever structure, and therefore the arms had to be thickened to withstand loads, twisting, pulling, bending, and other forces on the arms. When the arms are thickened, the weight of the aircraft increases in proportion to the thickness of the arms, and the aircraft's flight range is reduced accordingly.

[0006] In view of the above circumstances, the present invention provides an aircraft or the like that can improve the strength of the rotor frame as a whole without increasing the thickness of the rotor frame.

[0007] According to one aspect of the present invention, there is provided an aircraft comprising an airframe, a plurality of rotor frames, a motor, and a rotor, wherein the airframe supports the plurality of rotor frames, the plurality of rotor frames having contact portions that are contact points at which the plurality of frames including the rotor frames are connected, the motor is supported at the contact portions and configured to be able to transmit a driving force to the rotor to rotate the rotor, and the rotor is supported at the contact portions and configured to be able to rotate using the driving force.

[0008] The rotor frame supports the motor and rotor at contact points where they are connected to other frames. In other words, because the motor and rotor, which are heavy objects, are supported using multiple frames, the weight of the motor and rotor can be distributed among the frames. Therefore, according to one aspect of the present invention, it is not necessary to thicken the rotor frame to withstand loads, twisting, tension, bending, and other forces on the rotor frame. This reduces the weight of the aircraft, thereby extending the aircraft's range.

[0009] According to another aspect of the present invention, there is provided an aircraft comprising an airframe, a plurality of rotor frames, a motor, and a rotor, wherein the airframe supports the plurality of rotor frames, each of the rotor frames being formed in a direction extending radially from the airframe, the motor is supported by the rotor frame and configured to be able to transmit to the rotor a driving force for rotating the rotor, the rotor is supported by the rotor frame and configured to be rotatable using the driving force, the plurality of rotor frames have auxiliary frames interposed and connected between a set of adjacent rotor frames, each set of rotor frames being a set of rotor frames extending from the same base end, the base end being an end corresponding to the connection portion between the airframe and the rotor frames.

[0010] The rotor frames are connected to each other via an auxiliary frame. Therefore, the motor and rotor, which are heavy objects, are not supported by only one rotor frame, but are supported by the rotor frames to which they are connected. In other words, the weight of the motor and rotor can be distributed among multiple rotor frames. Therefore, according to another aspect of the present invention, there is no need to thicken the rotor frame in order to provide a structure that can withstand loads, twisting, pulling, bending, and other forces on the rotor frame. This leads to a reduction in the weight of the aircraft, and ultimately to an extension of the aircraft's range.

[0011] According to this aspect, the strength of the rotor frame as a whole can be improved.

[0012] FIG. 1 is a perspective view showing an overview of the aircraft 100. FIG. 2 is a partially enlarged plan view of a portion of the aircraft 100. FIG. 3 is a partially enlarged bottom view of a portion of the aircraft 100. FIG. 4 is a plan view (1) of the aircraft 100. FIG. 5 is a plan view (2) of the aircraft 100. FIG. 6 is a front view of the aircraft 100.

[0013] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the accompanying drawings. Various features shown in the following embodiments can be combined with each other.

[0014] 1. Overview of the Air Vehicle 100 In Section 1, an overview of the air vehicle 100 will be described.

[0015] Fig. 1 is a perspective view showing an overview of the aircraft 100. Fig. 2 is a partially enlarged plan view of a portion of the aircraft 100. Fig. 3 is a partially enlarged bottom view of a portion of the aircraft 100. Fig. 4 is a plan view (1) of the aircraft 100. Fig. 4 shows the arrangement of the rotor frame 120 among the frames.

[0016] The flying body 100 is a manned flying body capable of vertical takeoff and landing. The flying body 100 includes an airframe 110, multiple rotor frames 120, a motor 130, and a rotor 140. This embodiment is suitable for use with large rotor frames used in manned flying bodies. Here, the term "multiple rotor frames 120" refers to all of the rotor frames 120 included in the flying body 100 as a single entity. Furthermore, the term "rotor frame 120" refers to each individual rotor frame 120 that makes up the multiple rotor frames 120. These components will be further described.

[0017] The airframe 110 is located approximately at the center of the air vehicle 100. The airframe 110 supports a plurality of rotor frames 120. The airframe 110 has a passenger compartment (not shown) therein. The passenger compartment is configured to accommodate a crew member. The airframe 110 may be streamlined to reduce air resistance during forward flight.

[0018] The multiple rotor frames 120 are supported on the airframe 110 with the upper side of the airframe 110 as a support position. Each of the multiple rotor frames 120 is formed in a direction extending radially from a support position (base end 129) on the airframe 110. The multiple rotor frames 120 support the motor 130 and the rotor 140. The rotor frames 120 may be made of carbon fiber reinforced plastics (CFRP). The multiple rotor frames 120 may have a mesh structure in which multiple rod-shaped members (e.g., auxiliary frames 124 and 125 described below) are entangled with each other.

[0019] The motor 130 is supported by the rotor frame 120, with the lower side of the rotor frame 120 serving as a support position. The motor 130 is configured to be able to transmit a driving force to the rotor 140 to rotate the rotor 140. The motor 130 is connected to a power supply (not shown) via wiring 131, and generates a driving force by receiving a supply of electric power from the power supply.

[0020] The rotor 140 is supported by the rotor frame 120, with the upper side of the rotor frame 120 serving as a support position. The rotor 140 is configured to be rotatable at the position supported by the rotor frame 120 using a driving force transmitted from the motor 130. The rotor 140 generates buoyancy and thrust for the flying body 100 when rotated by the motor 130. The rotation speed and direction of the rotor 140 are controlled by a control system (not shown).

[0021] The multiple rotor frames 120 have auxiliary frames 124 and 125 interposed between and connected to adjacent rotor frames 120 in a set, as well as a reinforcing frame 128. Here, one set of rotor frames 120 refers to a set of rotor frames 120 extending from the same base end 129, and is, for example, a set of frames made up of rotor frames 120A, rotor frames 120B, and rotor frames 120C shown in Fig. 4. The base end 129 is an end portion corresponding to the connection portion between the airframe 110 and the multiple rotor frames 120.

[0022] The auxiliary frames 124 and 125 have the same function, material, and shape as the rotor frame 120. Therefore, the rotor frame 120, the auxiliary frames 124, and the auxiliary frames 125 are also collectively referred to as "frames."

[0023] The multiple rotor frames 120 have contact portions 151, 152, and 153 (hereinafter also collectively referred to as "contact portions 150") which are contact points where the rotor frames 120, auxiliary frames 124, and auxiliary frames 125 are connected. At contact portion 151, two frames (one rotor frame 120 and one auxiliary frame 125) are connected. At contact portion 152, three frames (one rotor frame 120 and two auxiliary frames 125) are connected. At contact portion 153, five frames (three rotor frames 120 and two auxiliary frames 124) are connected.

[0024] The multiple rotor frames 120 support the motor 130 and the rotor 140 at the contact portions 150. In other words, the motor 130 and the rotor 140 are each supported at the contact portions 150. That is, the multiple rotor frames 120 support the motor 130 and the rotor 140 at the portions where the rotor frames 120 are connected to the auxiliary frames 124 or the auxiliary frames 125. Therefore, the contact portions 150 (the portions where the rotor frames 120 are connected to the auxiliary frames 124 or the auxiliary frames 125) are portions where loads are concentrated in the multiple rotor frames 120. Here, by using the aspect of this embodiment, it is possible to reinforce the portions where the loads of the motor 130 and the rotor 140 are applied.

[0025] There is a trade-off between the weight of the multiple rotor frames 120 and the degree of distribution (reinforcement) of the force applied to the contact section 150. Therefore, it is preferable that the contact section 150 is a contact point where two to five frames are connected. According to this embodiment, it is possible to achieve a good balance between distribution of the force applied to the rotor frames 120 and a reduction in the weight of the aircraft 100.

[0026] It is preferable that the contact portion 150 is included in all of the rotor frames 120. According to this aspect, the force applied to the rotor frames 120 can be distributed among all of the rotor frames 120.

[0027] 2. Shape of the Multiple Rotor Frames 120 In Section 2, the shape of the multiple rotor frames 120 of this embodiment will be described.

[0028] Fig. 5 is a plan view (2) of the flying body 100. Fig. 6 is a front view of the flying body 100. Fig. 5 shows the arrangement of the auxiliary frames 124 and 125 among the frames.

[0029] The multiple rotor frames 120 are formed in a curved surface shape (hereinafter also referred to as "imaginary curved surface 160") that covers the airframe 110. The multiple rotor frames 120 have a total of eight contact points (contact points 154 and contact points 156) on the outer periphery 126. The contact points 154 and contact points 156 are formed at end points 161 of each rotor frame 120 that correspond to the ends of the imaginary curved surface 160. In other words, the contact points 154 and contact points 156 are provided at a total of eight locations on the outer periphery 126. Here, the outer periphery 126 is formed by connecting the end points 161 of the rotor frames 120.

[0030] Adjacent contact portions 154 are connected to each other via the frame. The contact portions 154 located on the outer periphery 126 are connected to the auxiliary frame 125. In this way, due to the relationship between the contact portions 154 located on the outer periphery 126 and the auxiliary frame 125, the outer periphery 126 of the multiple rotor frames 120 is formed into an octagonal shape in a plan view.

[0031] The above will be explained using another expression. The multiple rotor frames 120 have a total of eight free ends at the end (outer periphery 126) of the imaginary curved surface 160. The free ends are ends of the rotor frames 120, and are ends opposite the end (base end 129) corresponding to the connection portion between the rotor frames 120 and the airframe 110. The free ends correspond to the end 161 and the positions of the contact points 154 (contact points 156). The auxiliary frames 125 are interposed between and connected to the free ends adjacent to each other. In this way, due to the relationship between the free ends of the rotor frames 120 located on the outer periphery 126 and the auxiliary frames 125, the outer periphery 126 formed by connecting the free ends of the rotor frames 120 is formed into an octagonal shape in a plan view.

[0032] According to this aspect, it is possible to reduce the amount of deformation of the rotor frame 120 due to the force applied to the rotor frame 120, and to provide an aircraft 100 with a good balance between strength and weight.

[0033] The connection portions between the rotor frames 120 and the auxiliary frames 124 form contact portions 155. The multiple rotor frames 120 have a total of four contact portions 155 on the inner periphery 127. The inner periphery 127 indicates a position including the four contact portions 155 and the four auxiliary frames 124. The auxiliary frames 124 are connected to adjacent sets of rotor frames 120 by being interposed between their approximate centers from the base end 129 to the free end. Here, the free end is the end of one set of rotor frames 120 (i.e., the end of rotor frame 120B and rotor frame 120C) that is opposite the base end 129 (i.e., contact portion 154 or contact portion 156).

[0034] The frame is configured so as not to be present between two contact points 156 located in the forward direction of the airframe 110 (in the direction of the arrow 101). In other words, the auxiliary frame 125 is configured so as not to be present between two free ends (synonymous with the contact points 156) located in the forward direction of the airframe 110 (in the direction of the arrow 101).

[0035] According to this aspect, forward visibility can be ensured when the flying object 100 is flying.

[0036] The reinforcing frame 128 is arranged along the rotor frame 120 (rotor frame 120A) connected to the airframe 110 and the rotor frame 120 (rotor frame 120B) extending outward from the rotor frame 120. The reinforcing frame 128 may be arranged across two or more rotor frames 120. The reinforcing frame 128 is provided to reduce forces such as load, twisting, tension, and bending applied to the rotor frame 120 connected to the airframe 110. The reinforcing frame 128 may have a shape thicker than the rotor frame 120. The reinforcing frame 128 increases the overall strength of the multiple rotor frames 120, thereby contributing to stable flight of the aircraft 100.

[0037] According to this aspect of the present embodiment, it is possible to distribute the force applied to the multiple rotor frames 120. This allows the thickness of the rotor frames 120 to be reduced, thereby reducing the weight of the aircraft 100. Therefore, it is possible to extend the range of the aircraft 100.

[0038] Although the embodiment of the present invention has been described above, the present invention is not limited to this and can be modified as appropriate within the scope of the technical idea of ​​the invention.

[0039] 3. Modifications Modifications of this embodiment will be described in Section 3. The following modifications can be combined as appropriate.

[0040] In the present embodiment, one set of rotor frames 120 has been described as being a set of rotor frames 120A, 120B, and 120C, but is not limited to this. For example, it may be a single rotor frame, a set of two rotor frames, or a set of four or more rotor frames.

[0041] The number of frames connected at the contact portion 150 is not particularly limited as long as it is 2 or more. Specifically, the number may be, for example, 2, 3, 4, 5, 6, 7, 8, 9, or 10, or may be within a range between any two of the numerical values ​​exemplified here.

[0042] In the present embodiment, the adjacent contact portions are described as being connected to each other via a frame, but this is not limiting. It is sufficient that one or more sets of adjacent contact portions are connected to each other via a frame. For example, contact portion 154 may be connected to another contact portion 154, and contact portion 156 may not be connected to another contact portion 156. Furthermore, all sets of adjacent contact portions may be connected to each other via a frame.

[0043] 6, the rotor frames 120 are described as being formed in a curved shape that covers the airframe 110 when the air vehicle 100 is viewed from the front, but this is not limited to this. The rotor frames 120 are also formed in a curved shape that covers the airframe 110 when the air vehicle 100 is viewed from any angle or viewpoint.

[0044] 4. Others The present invention may be provided in the following forms.

[0045] (1) An aircraft comprising an airframe, a plurality of rotor frames, a motor, and a rotor, wherein the airframe supports the plurality of rotor frames, the plurality of rotor frames having contact portions that are contact points where a plurality of frames including the rotor frames are connected, the motor is supported at the contact portions and configured to be able to transmit a driving force to the rotor that rotates the rotor, and the rotor is supported at the contact portions and configured to be able to rotate using the driving force.

[0046] (2) In the aircraft described in (1) above, the contact portion is a contact point to which two or more and five or less of the frames are connected.

[0047] (3) The aircraft described in (1) or (2) above, wherein the contact portions are included in all of the rotor frames.

[0048] (4) In the aircraft described in any one of (1) to (3) above, the multiple rotor frames are formed in a curved shape that covers the aircraft, the multiple rotor frames have a total of eight contact points, the contact points are formed at the ends of each rotor frame corresponding to the curved ends, one or more sets of adjacent contact points are connected via the frame, and the outer periphery formed by connecting the ends of the rotor frames is octagonal in plan view.

[0049] (5) An aircraft as described in (4) above, wherein the frame is configured so as not to be located between the two contact points located at the front of the aircraft.

[0050] (6) An aircraft described in any one of (1) to (5) above, wherein the aircraft is a manned aircraft.

[0051] (7) An aircraft comprising an airframe, a plurality of rotor frames, a motor, and a rotor, wherein the airframe supports the plurality of rotor frames, each of the rotor frames being formed in a direction extending radially from the airframe, the motor being supported by the rotor frame and configured to be able to transmit to the rotor a driving force that rotates the rotor, the rotor being supported by the rotor frame and configured to be able to rotate using the driving force, the plurality of rotor frames having auxiliary frames interposed and connected between adjacent sets of the rotor frames, the set of rotor frames being a set of rotor frames extending from the same base end, the base end being an end corresponding to the connection portion between the airframe and the rotor frame.

[0052] (8) In the aircraft described in (7) above, the auxiliary frame is connected between the approximate center portions of the rotor frames of the set adjacent to each other between the base end and the free end, and the free end is an end of the rotor frame of the set opposite the base end.

[0053] (9) In the aircraft described in (7) or (8) above, the auxiliary frame is interposed between and connected to the free ends of the rotor frames of the set adjacent to each other, and the free ends are the ends of the rotor frames of the set opposite the base ends.

[0054] (10) In the aircraft described in any one of (7) to (9) above, the plurality of rotor frames are formed in a curved shape that covers the aircraft, the plurality of rotor frames have a total of eight free ends at the curved ends of the rotor frames, the free ends are ends of the rotor frames of the set that are opposite the base end, the auxiliary frame is interposed between and connected to adjacent free ends, and the outer periphery formed by connecting the free ends is octagonal in plan view.

[0055] (11) An aircraft as described in (10) above, wherein the auxiliary frame is configured so as not to be located between the two free ends located at the front of the aircraft.

[0056] (12) In the aircraft described in any one of (7) to (11) above, the plurality of rotor frames support the motor and the rotor at the portion where the rotor frame and the auxiliary frame are connected.

[0057] (13) The flying object according to any one of (7) to (12) above, wherein the flying object is a manned flying object. Of course, this is not a limitation.

[0058] 100: aircraft, 101: arrow, 110: fuselage, 120: rotor frame, 120A: rotor frame, 120B: rotor frame, 120C: rotor frame, 124: auxiliary frame, 125: auxiliary frame, 126: outer periphery, 127: inner periphery, 128: reinforcing frame, 129: base end, 130: motor, 131: wiring, 140: rotor, 150: contact portion, 151: contact portion, 152: contact portion, 153: contact portion, 154: contact portion, 155: contact portion, 156: contact portion, 160: virtual curved surface, 161: end portion

Claims

1. An aircraft comprising an airframe, a plurality of rotor frames, a motor, and a rotor, wherein the airframe supports the plurality of rotor frames, the plurality of rotor frames have contact portions which are contact points at which a plurality of frames including the rotor frames are connected, the motor is supported at the contact portions and configured to be capable of transmitting a driving force to the rotor to rotate the rotor, and the rotor is supported at the contact portion and configured to be rotatable using the driving force.

2. An aircraft according to claim 1, wherein the contact portion is a contact to which two or more and five or less of the frames are connected.

3. An aircraft according to claim 1 or 2, wherein the contact portion is included in all of the rotor frames.

4. An aircraft as claimed in any one of claims 1 to 3, wherein the rotor frames are formed in a curved shape that covers the aircraft, the rotor frames have a total of eight contact points, the contact points are formed at the ends of each rotor frame corresponding to the curved ends, one or more sets of adjacent contact points are connected via the frame, and the outer periphery formed by connecting the ends of the rotor frames is shaped like an octagon in a plan view.

5. The flying vehicle according to claim 4, wherein the frame is configured so as not to be present between the two contact points located at the front of the vehicle.

6. The flying object according to any one of claims 1 to 5, wherein the flying object is a manned flying object.

7. An aircraft comprising an airframe, a plurality of rotor frames, a motor, and a rotor, wherein the airframe supports the plurality of rotor frames, each of the rotor frames being formed in a direction extending radially from the airframe, the motor is supported by the rotor frame and configured to be capable of transmitting a driving force for rotating the rotor to the rotor, and the rotor is supported by the rotor frame and configured to be rotatable using the driving force, the plurality of rotor frames have auxiliary frames interposed and connected between a set of adjacent rotor frames, the set of rotor frames being a set of rotor frames extending from the same base end, and the base end being an end portion corresponding to a connection portion between the airframe and the rotor frames.

8. An aircraft as described in claim 7, wherein the auxiliary frame is connected between the approximate center portions of the rotor frames of the set adjacent to each other between the base end and the free end, and the free end is an end portion of the rotor frames of the set opposite the base end.

9. An aircraft as described in claim 7 or 8, wherein the auxiliary frame is interposed between and connected to each free end of the rotor frames of the set adjacent to each other, and the free ends are ends of the rotor frames of the set opposite to the base ends.

10. An aircraft as claimed in any one of claims 7 to 9, wherein the rotor frames are formed in a curved shape that covers the aircraft, the rotor frames have a total of eight free ends at the curved ends, the free ends being ends of the set of rotor frames opposite the base end, the auxiliary frame is interposed between and connected to adjacent free ends, and the outer periphery formed by connecting the free ends is octagonal in plan view.

11. The flying vehicle according to claim 10, wherein the auxiliary frame is configured so as not to be present between the two free ends located in the front of the airframe.

12. An aircraft according to any one of claims 7 to 11, wherein the plurality of rotor frames support the motor and the rotor at a portion where the rotor frame and the auxiliary frame are connected.

13. The flying vehicle according to any one of claims 7 to 12, wherein the flying vehicle is a manned flying vehicle.

Images